JPH0660601B2 - Multiple propellant solid rocket engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention utilizes a plurality of propellants and has the ability to repeatedly start, stop, and restart, and further, the attitude of the rocket in flight. Controlling solid propellant rocket engine. This rocket engine is characterized by high thrust in addition to high impulse acceleration in part, and also requires a series of meter or throttle stop and restart operations as required.

[Conventional technology]

Solid propellant rocket engine proplasi (proplusi
ve) full capacity is usually consumed during the burning of one solid propellant grain. This is because once a grain of solid propellant is ignited, it is difficult to stop the combustion process and usually the entire grain is consumed.

In the prior art, a solid propellant rocket engine with one or more ignition capabilities, i.e. two or more centralized units, i.e. a layer or zone of solid propellant in the combustion chamber with a flame suppression barrier separating the layers. Proposes to prepare a rocket engine with "start-stop-restart" capability. This flame suppression barrier then limits the combustion to a single layer or zone, while the adjacent layers are made of a material that is rupturable enough to be ignited. The combustion of each layer produces thrust in the form of discontinuous pulses.

One such device that provides a rocket engine that can be ignited more than once is disclosed in U.S. Pat. No. 3,293,855 issued Dec. 27, 1966 to WE Katchill et al. Therein, a pyrotechnical and electrically ignitable film is provided between the layers for ignition and, if desired, between adjacent layers. Similarly, Thomas W. Bastian and others 1982
U.S. Pat. No. 4,357,795, issued Nov. 9, 1999, discloses a solid rocket fuel having multiple fuel layers that can be independently ignited. The layered portions can be installed end to end within the casing.

Other such devices are disclosed in U.S. Pat. No. 3,564,845 granted to IH Friedman et al. On February 23, 1971 and 3,568,448 granted to GE Web, Jr. Mar. 9, 1971, among which: One of the two solid propellant concentration layers separated by the flame suppression barrier is ignited by an igniter extending through the rocket engine nozzle into the combustion chamber. The other layers are ignited by a gas generator connected by extension tubes to the crown end of the combustion chamber. A rupturable diaphragm seal and perforated support member assembly are provided to isolate the gas generator from the engine combustion chamber during the initial rocket propellant bed combustion. U.S. Pat. No. 3,677,010 granted to C, W, Bigland on July 18, 1972
Discloses a dual thrust level rocket engine with restart capability, including an oxidizer supply and multiple injectors for supplying oxidizer to fuel particles. U.S. Patent No. 3,677,010 granted to RH Finck et al. On July 18, 1972 is
Disclosed is a solid fuel rocket engine having grains that make up a plurality of individual concentrating layers separated by a liner that has insufficient oxidizer to maintain combustion. The liner causes the auto-ignitable liquid oxidizer to be injected to ignite the exposed liner layer and the next propellant layer which should expand the area of the rocket. U.S. Pat. No. 3,457,727 granted to JR Munger on July 29, 1969 discloses a solid fuel rocket engine that utilizes solid propellant and liquid oxidizer injected at the rear of the engine. U.S. Pat. No. 3,452,544, granted to RL Grick et al. On July 1, 1969, is a single solid with thrust-up and hold-up capability obtained by a gas generator or cooling mechanism assembled in a rocket engine. A solid propellant rocket engine is disclosed with propellant particles.

U.S. Pat. No. 3,826,087, granted to Alan J. McDonald on July 30, 1974, discloses a solid propellant rocket in which gas generators are mixed to obtain rocket thrust and generate gas for combustion.

GF Mangnum granted US patent on September 12, 1967
3,826,087 and WC Acock, licensed November 28, 1967, 3,354,647, are similar devices that allow liquid fuel to enter the combustion chamber for flame suppression barriers and destruction and ignition of adjacent layers of propellant. Is disclosed.

All of the above-mentioned prior art features consist in providing a single combustion chamber for multiple concentrated solid propellant layers in a zone, destroying the flame suppression barrier between the layers and advancing to the next adjacent layer. And igniting adjacent layers using a relatively complex igniter to ignite and destroy the barrier. Friedman, Jr., et al. And Web, Jr. 'S patent includes a destructible diaphragm and a perforated support member that tends to carry debris into the combustion chamber when destroyed and individually disassembled. The Mangham and Aycock patents allow the entry of liquid fuel into the combustion chamber.

U.S. Pat. No. 4,98,603, filed May 26, 1983 by M. Fling et al. And assigned to the assignee of the present invention, is capable of igniting more than once and is manufactured in a concentrated or continuous manner to produce holes. Disclosed is a solid propellant rocket engine that includes the use of a plurality of combustion chambers separated by open partitions, each of which contains an individually related propellant. A pressure responsive diaphragm means positioned in the first combustion chamber covers the perforations in the bulkhead and provides communication between the combustion chambers when the pressure present in the first combustion chamber is substantially higher than that in the adjacent chambers. When the pressure is blocked and the pressure in the combustion chamber reverses, communication between the combustion chambers is allowed. Numerous other devices aimed at the controlled flight of solid propellant rocket engines include:
It is disclosed in the prior art by the following US patents.

3,811,380 JP Grass 3,668,872 AT Kampu, etc. 3,494,130 S. Zeeman 3,457,726 J. Trotel 3,434,287 L. Cavigny 3,398,537 JE Picender 3,349,565 AE Williams 3,349,563 EL Taylor 3,248,875 RD Walcott 3,266,237 CJ Crowell, etc. Inherent limitations in all different forms of engine, i.e. lack of ability to provide high thrust and / or high impulse augmentation pulses associated with a series of stop / restart throttle actuations,
Is being discussed.

[Problems to be Solved by the Invention]

It is a primary object of the present invention to provide a solid propellant rocket engine having thrust and / or high impulse boost pulses associated with a series of controlled stop and restart throttle valve operations. Another object of the invention is to utilize multiple propellants and, if desired, the ability to stop / restart as well as a gas generator controlled stop / start post-stage to provide attitude control. It is to provide a solid propellant rocket engine consisting of a speed-up engine with a built-in speed-up engine.

Another object of the present invention is to provide an independent thrust device capable of performing both speed-up and rear-stage speed-up operations.

Still another object of the present invention is to provide a reliable and relatively inexpensive solid propellant rocket capable of performing multistage stop and restart combustion.

Yet another object of the present invention is to provide a solid propellant rocket engine of minimum volume and weight capable of providing accelerated and repetitive post-accelerated ignition.

Another object of the present invention is to provide a solid propellant rocket engine incorporating a gas generator with a throttle valve mechanism in addition to complete extinguishment depending on increased operational flexibility and requirements.

It is another object of the present invention to provide a built-in solid propellant rocket engine with accelerated and repetitive post-acceleration thrust with extreme package flexibility and performance flexibility.

Yet another object of the present invention is to provide a solid propellant rocket engine that has an integrated Attitude Control System (ACS) as an additional feature, thereby allowing dual use of gas generator products. .

[Means for Solving the Problems]

In order to achieve these and other objects of the present invention, a rocket engine having a plurality of casings for enclosing an initial speed increasing engine, a rear speed increasing engine, and a reignition and attitude control device for the rear speed increasing engine. Gas generator means are provided for generating the gas used as a source of motion. The speed-up engine and the post-stage speed-up engine are contained within the same enclosure, but are operatively separated by an internal bulkhead. Rocket engines include multiple nozzles. At least one nozzle is located at the rear of the speed-up engine, and another nozzle is located in the internal partition wall intermediate the speed-up engine and the rear speed-up engine.

〔Example〕

In FIG. 1, reference numeral 10 is used to generally indicate a solid propellant rocket engine.

The solid propellant rocket engine 10 includes a first rocket engine casing 12, which is cylindrical and has a solid propellant booster engine 14 and an extinguishable solid propellant rear stage booster engine 16 therein. Including. The speed-up engine 14 and the rear speed-up engine 16 include combustion chambers associated therewith, particularly a speed-up engine room 18 and a rear-speed speed-up engine room 20, respectively. The speed-increasing engine room 18 is within the area of the first enclosing portion 22 of the engine casing 12, and the rear speed-increasing engine room 20 is within the area of the second enclosing portion 24 of the casing 12.
Formed within the area of. Casing 12 is made of any suitable material with each enclosure 22 and 24 comprising a liner of synthetic rubber, preferably adhered to its inner wall.

The enclosures 22 and 24 share a common internal heat or flame resistance to isolate the septum 26. Isolation 26 includes a hole therein that forms a post-acceleration pressure control nozzle 28.
The nozzle 28 serves to increase the speed of the engine 14 as described below.
The communication between the rear speed increasing engine 16 and the rear speed increasing engine 16 is enabled during the operation of the rear speed increasing engine. The repetitive ignition capability of the post-acceleration engine 16 is one of the keys to the successful operation of the multipropellant solid rocket engine of the present invention. The nozzle 28 is important for controlling the ratio of the pressure in the rear stage speed increasing engine chamber 20 to the decline rate of the pressure during the operation of the rear stage speed increasing engine 16. Therefore, the area of the holes in the control nozzle 28 has a significant effect on correct post-stage boost engine operation. The hole area of the nozzle 28 is shown as A _2, as shown in FIG.

Septum 26 includes a rupturable septum disk or rupturing diaphragm 30, which initially occludes a post-acceleration pressure control nozzle 28, as best shown in FIG. 2A. The diaphragm 30 is supported within the two-part plug 31, 32 of insulation that is press fit into the area of the hole 28 and is held therein by a suitable O-ring 29 and during operation of the speed-up engine 14. The pre-ignition of the rear-stage acceleration engine 16 is prevented from being prematurely ignited. Immediately prior to operation of the rear speedup engine 16, the isolated burst diaphragm 30 needs to be destroyed or otherwise removed from the bulkhead 26. This is a blasting device 33 positioned adjacent to the diaphragm 30.
And by means of electrical or pyrotechnical fuse means, not shown. The explosion of the blasting device 33 destroys the diaphragm 30, thereby opening the post-acceleration pressure control nozzle 28. In one preferred embodiment of the invention, the blasting device 33 includes a rupture diaphragm 3 as shown in FIG. 2B.
It consists of a linear charge 35 of the known type, which is generally formed for the 0 contour, so that in an explosion the bursting diaphragm 30 is relatively cleanly separated from the septum 26. In another embodiment of the invention, the linear charge is pierced in the septum 26 with sufficient explosive force,
It is shaped to thereby form the pressure control nozzle 28.

As shown in FIG. 1, the solid-state speed-increasing engine 14 includes hollow high-energy accelerating energy propellant particles 34 in the inner region of the accelerating engine that prepares an initial high-thrust or high-impulse accelerating pulse. The propellant particles 34 are placed in or bound to the isolation layer on the inner wall of the enclosure 22. The speed increasing engine 14 includes a speed increasing engine igniter 36 that ignites the speed increasing engine propellant particles 34 at its trailing end. The igniter 36 includes an electrical detonator in contact with the pyrotechnical material so that when the detonator is ignited, the pyrotechnical material that ignites the propellant particles 34 is ignited. Any one of a number of pyrotechnical materials, 25% by weight boron
And igniter containing a granular mixture of 75% by weight potassium nitrate
Used within 6.

Accelerating the engine 14 is in its rear position, A ₃ in FIG. 3
And includes a nozzle 38 having a working area or throat in a convergent-dispersive form as shown. At that time, the area A ₃ is the area A ₂ of the nozzle 28 of the post-stage acceleration engine 16.
Greater than. In the preferred embodiment, the nozzle 38 is all-axis moveable and is adapted to include the rocket engine 10 with thrust vector control capabilities. The nozzle 38 is controllably operated by a nozzle actuator 40.

The structure and operation of the nozzle 38 and the actuator 40 are similar to those of Thomas E. Bolner for “internally operated spherical bearings”.
It is similar or identical to that discussed in US Pat. No. 4,435,023, issued March 6, 1984, and assigned to the assignee of the present invention.

The extinguishable hollow propellant particles 42 are installed in the area of the enclosing portion 24 of the rear speed increasing engine. The propellant particles 42 are loaded or bonded within the isolation layer or liner on the inner wall of the enclosure 24. The shape of the front end of the grain 42 preferably matches the curvature of the front inner wall of the case 24. The propellant particles 42 are from the crown end 44 of the surrounding portion 24 to the partition wall 26,
Alternatively, when it is desired to install the desired amount of extinguishable propellant in the engine compartment 20, it is otherwise extended. A diffuser 46 installed in the engine compartment 20 distributes the ignitable gas medium onto the exposed surface of the propellant particles 42.
The diffuser 46 is installed within the range of the rear-stage acceleration engine room 20 adjacent to the front inner wall surrounding portion 24. The diffuser 46 inlet communicates with the outside of the first engine casing 12 as discussed further below.

A second engine casing 48 forming a third enclosure 49 containing a gas generator 50 is installed adjacent to the first engine casing 12. The gas generator 50 includes a gas generator propellant particle 52 and a gas generator multiple igniter 54 of the known electric arc or bridge wire type. The gas generator propellant granules 52 constitute a propellant having a combustion temperature in the range 2000-3000 ° F. The typical gas generator propellant granules used are 3000 ° HTPB / HMX. The gas generator 52 is molded or placed inside the casing 48 opposite the external hole 56 for exhaust from the gas generator 50 during combustion of the propellant particles 52.

The multi-port gas generator flow control valve 58 is located midway between the first casing 12 and the second casing 48 and is set so that it controls the gas flow from the gas generator 50. The flow control valve 58 has a large number of inlets and outlets, and the gas flow from the generator 50 through the branch pipe 60 to the attitude control device (ACS) 62 or the diffuser 46 in the engine room 20 of the post-accelerating engine 16. To prepare. When directed to the diffuser 46, the gas generator flow ignites and reacts the propellant with the extinguishable rear stage engine to provide an increased specific impulse. The increased specific impulse results from the secondary combustion of the gas generant gas mixed with the post-acceleration propellant gas (increasing the specific impulse from 40 to 60 seconds is dependent on the gas generator propellant 52 and the post-acceleration engine propellant). 42 can be obtained by a suitable combination of gases from 42).

The pressure in the post-acceleration engine 16 is controlled by holes 28 in the internal bulkhead 26 which serve as post-acceleration pressure control nozzles. To extinguish the post-acceleration engine, the generated gas flow is diverted to the attitude control device 62 through the gas generator flow control valve 58 and the branch pipe 60, or the combustion of the gas generating propellant 52 in the generator 50 is ended. To be achieved. The operation of the gas generator 50 is terminated by, for example, the valve 5
This is done by opening a large valve area of 8 as shown at outlet 66. The outlet 66 then allows a rapid pressure drop of the gas generator 50 to the atmosphere, thereby causing the gas generator propellant 52 to extinguish.

As previously mentioned, the gas from the gas generator 50 is directed by the branch tube arrangement 60 towards the various outlets or propulsion pieces 64 used to control attitude, roll, or direction.

Therefore, during operation, the multi-propellant solid rocket engine depends on the speed increasing engine 14 integrated with the rear speed increasing engine 16 and the combustion is controlled by the gas generator 50 in the rear speed increasing engine 16, so that the rear speed increasing engine 16 is operated. The engine 16 generally shuts down, restarts, and repeats throttling when desired. Further, the gas generator 50 also repeats the operation of stopping and restarting as a whole. When the gas generator 50 is deactivated, all propellant particles 34, 42, and 52 are completely extinguished, and the propellant particles 34 are totally consumed during the pre-operation of the speed-up engine 14. . The accelerating igniter 36 ignites the high energy accelerating propellant particles 34 to operate the accelerating engine 14 and prepares a high thrust or high impulse accelerating pulse. The all-axis moveable nozzle 38 provides thrust vector control of the rocket with its associated nozzle actuator 40. Insulating inner partition wall 2 during operation of acceleration energy
6 separates the speed-up engine 14 from the rear speed-up engine 16 to prevent premature ignition of the rear speed-up engine 16 in view of the high temperatures that occur during operation of the speed-up engine.

When the combustion of the speed-up engine propellant particles 34 is completed, the speed-up engine room 18 from that point onwards becomes the rear-stage speed-up engine
, So that the movable nozzle 38 remains effective to provide the necessary thrust vector control. Blasting device 3 prior to the operation of the latter stage acceleration engine 16
2 is driven to either rupture the rupturing diaphragm 30 or to drill a desired sized hole in the internal septum 26 for the nozzle 28. The plurality of igniters 54 are then driven to ignite the gas generator grains 52. The generated gas flow is conveyed through a multi-port flow control valve 58 to a diffuser 46 with a valve 58 that controls both the pressure and flow velocity of the generated gas flow. The latter-stage speed increasing engine propellant powder 42 is provided in the diffuser 46.
When the gas dispersed in the latter-stage acceleration engine chamber 20 comes into contact with it, it is ignited. The ignition and reaction of the gas flow through the diffuser 46 causes the particular impulses increased by the secondary combustion of the extinguishable propellant particles 42 of the post-acceleration engine and the evolved gas mixed with the gas of the propellant particles 42. prepare. As already mentioned, a significant specific impulse increase from 40-60 seconds can be obtained by a suitable combination of gas generator and post-acceleration engine propellant gas.

The rear speed increasing pressure control nozzle 28 is used for the rear speed increasing engine 16
Controls the pressure of the rear stage acceleration engine during the operation of. The combustion of the post-accelerating engine propellant particles 42 either directs the direction of the gas from the generator 50 to the attitude control device 62 via the gas generator flow control valve 58, or opens the valve outlet 66 directly to the atmosphere. It is extinguished by diverting the evolved gas stream therethrough, which causes a rapid pressure drop in the gas generator chamber, which subsequently extinguishes the combustion of the gas generant propellant particles 52. Such a rapid pressure drop requires a relatively large area for the outlet 66.

As described above, the repeated stop and start of the post-stage acceleration engine 16 is performed by the nozzle that controls the ratio of the pressure and the pressure decay in the post-stage acceleration engine chamber 20 to the post-stage acceleration engine pressure control nozzle area A ₂ . It represents a sensitivity of 28. The area A ₂ of the control nozzle 28 is also the ratio of the combustion surface area to the throat area (for convenience, hereinafter referred to as Kn), and the engine free volume to the throat area ratio (for convenience, hereinafter L).
Control). According to the present invention, these are two control parameters for designing the shape of the rocket engine, which can be extinguished during operation of the post-acceleration engine. The following examples of these parameters provide the fire fighting capability of the rocket engine of the present invention.

Vacancy 1 of the speed increasing engine 14 during operation of the rear speed increasing engine
The throat area A ₃ of the nozzle 38 that is movable in all axes, which is added to FIG. 8, controls the thrust level and the thrust decay transient time of the post-stage acceleration engine 16, but since the area A ₃ is larger than the area A ₂ , It does not affect the fire extinguishing ability of the rear stage speed increasing engine 16.

The partition wall 26 is an "off cycle" of the post-stage acceleration engine 16.
Prevents thermal radiation of the rear-stage acceleration engine propellant particles 42
It should also be mentioned that it prevents accidental ignition of the post-acceleration engine grain 42.

For the above work to be successful, a constant relationship between pressure and throat area must be maintained. These relationships are first
Explained in the table and below in relation to FIG.

As can be seen from Table 1, the speed-up engine operation uses any propellant or engine geometry that is the best within the constraints of the selected equipment, without considering the speed-up engine operating pressure. be able to. The same applies again for gassing working pressure during attitude control, unless the structural constraints of the container are again exceeded. Important to the operation of the present invention is the understanding that the evolved gas flow through the post-acceleration pressure control nozzle 28 must always be a closed flow. The working area of the flow control is preferably variable,
Different areas and / or flow direction and attitude control devices and rear speedup engines are provided with throttling action for operation. The flow control valve 58 is used for extinguishing the gas generator particles and for branching the pipe device 6.
A relatively large area outlet 66 is included for the closed position to disconnect the gas flow to the diffuser 46 via 0, thereby causing the post-accelerator engine propellant particles 42 to extinguish. Working pressure and the pressure decay transient time in the subsequent acceleration the engine 16 is controlled by the area A _2, rather than the area A _2, and also both Kn and L in the subsequent acceleration in the engine also prepared extinguishing in order to ensure that it is controlled by should do area a _2, the area a ₃ should be larger than the area a _2.

The choice of propellant for both the speed-up engine 14 and the gas generator 50 is not so limited, whereas the propellant 16 for the post-stage speed-up engine 16 is highly specific when mixed with the gas from the gas generator 50. Of the impulses of ## EQU2 ## and of being able to extinguish the gas as soon as the gas flow from the gas generator 50 is terminated. Carbon fluoride is unique in this respect.

Typically, the speed-up engine 14 utilizes a cruciform link, dual foundation, high energy propellant, or some high energy composite propellant. The extinguishing characteristics of the post-acceleration engine grain 42 in the preferred embodiment are made from non-metallized carbon fluoride type propellants. The gas generator propellant particles 52 are
3000 ° F HTPB / HMX gas generator propellant, or 2000-3000
Any gas generator propellant of ° F.

Using the figure and without limitation, several propellant particles 34, 42,
It is noted that the compositions of and 52 are composed of the following components.

Propellant granules 34; any propellant granules 42; 16% C ₇ fluoroacrylate
Binder 84% Ammonium Percolate Propellant Granules 52; 15% Hydroxyl terminated Polybutadiene Binder 85% Nitramine (HMX or RDX) A multi-propellant solid rocket engine is available in which a relatively unlimited selection of propellants is available as long as the impulse can be prepared, ie, extinguished as soon as the evolving gas stream is terminated.

〔The invention's effect〕

Accordingly, consistent with the present invention, a unique self-contained stepping machine is provided which performs both speed up and repetitive throttle post-stage speeding up operations, and optionally has an attitude control system as an additional feature. The apparatus of the present invention has the following advantages over prior art methods for performing both speed up and post speed up operations with separate thrust devices.

1. A single thrust device that performs both functions is more reliable and less expensive.

2. The volume and weight of the device for performing both the speed-up operation and the post-step speed-up operation are minimum.

3. The highest degree of combined use of solid propellants is available for both boost and post boost engine operation.

4. Due to the increased actuation flexibility, it has throttle actuation on demand and / or overall extinguishing capability with a gas generator.

5. Thrust ratio (fire reduction ratio) is extremely large. That is, the ratio of the speed increasing force to the latter speed increasing force is 20 or more, and the ratio of the speed increasing force to the ACS force is 100 or more.

6. The typical propellants used provide the highest specific impulses during acceleration, as well as the highest specific impulses obtained with extinguishable post-acceleration propellants that also have low pollution and official certification of low infrared.

As those skilled in the art will appreciate, if desired, other optional accessories can be incorporated into the single thrust device of the present invention to improve flexibility and performance versatility. Thus, for example: The second casing 48, which includes the gas generator 50, is, if necessary, the first casing 1 for a speed-up / post-speed engine.
Packages can be grouped along two sides.

2. The septum 26 is separated by a linear charge and, if desired, can be used as an expansion nozzle for the post-acceleration engine 16 (thrust vector control can be provided through an ACS thrust piece).

3. The rear speedup engine 16 can be used for additional speedup or operation.

4. One or more gas generators 50 can be added to extend the burning time and facilitate packaging. Thus, the additional gas generator 50 is packaged along with the lateral casing 12 and the entire assembly arranged to accommodate its use as a rocket or one-stage rocket in a cylindrical housing.

As will also be appreciated by those skilled in the art, embedded staged combustion devices have a number of thruster applications. In particular, this device is a strategic device that requires both acceleration and post-acceleration thrust, advanced ballistic interception missiles that require acceleration / maintenance / thrust and on / off operation, space engine for deploying satellites. , And has applications in tactical engines requiring acceleration / maintenance and / or pulsed engine operation.

While the exact structural details for the rocket of the present invention are not specifically shown, standard rocket construction techniques and methods provide rocket as long as dimensional requirements and ratios disclosed herein are met. Is made available for the manufacture of.

Upon reviewing this invention in detail, those skilled in the art will recognize that modifications can be made to the invention without departing from its spirit. Accordingly, the scope of the invention is illustrated,
It is not intended to be limited to the particular embodiments described. Rather, the scope of the present invention is intended to be determined by the appended claims and their equivalents.

[Brief description of drawings]

In summarizing the invention, reference will be made to the following drawings, which accompany the foregoing detailed description. FIG. 1 is a schematic diagram of a preferred embodiment of the present invention comprising a speed-up engine incorporating a stop-and-restart rear speed-up engine.
The former is controlled by a gas generator to provide repeated stop / restart capability as well as attitude control. FIG. 2A is a partial cross-sectional view showing an insulating plug bursting type diaphragm which is prepared between a speed increasing engine and a rear speed increasing engine and is driven to explode. FIG. 2B is a plan view showing a linearly formed blasting charge prepared on the bursting diaphragm of FIG. FIG. 3 is a diagram showing the physical relationships between the various components of the preferred embodiment of FIG. 10 ... rocket engine, 12 ... rocket engine casing, 14 ... speed increasing engine, 16 ... rear speed increasing engine, 18 ... speed increasing engine room, 20 ... rear speed increasing engine room, 22, 24 ...... First and second surrounding parts, 26 ... Partition wall, 28 ... Nozzle, 30 ... Bursting diaphragm, 31,32 ... Plug, 33 ... Explosion device, 34 ... Propellant granules, 36 ... Igniter, 38 ... Nozzle, 40 ... Nozzle actuator.

Claims (11)

[Claims] Claims: 1. A multi-propellant solid rocket engine characterized by including the following elements: (1) Solid propellant and propellant combustion gas is discharged from the first enclosure to provide thrust for the rocket engine. A first enclosure having a first combustion chamber including means for. (2) First ignition means for igniting the solid propellant. (3) A second enclosure associated with, but isolated from, the first enclosure having a second combustion chamber containing a solid extinguishable propellant. (4) A third enclosure having a third combustion chamber containing a gas generating propellant capable of generating a gas capable of igniting an extinguishable propellant. (5) A second ignition means for igniting the gas generating propellant. (6) Among them, contact with solid propellant capable of extinguishing, ignition,
And means for releasing the evolved gas in the second enclosure for the combustion reaction. (7) Intermediate pressure between the first and second enclosures to maintain a closed solid propellant combustion gas flow from the second enclosure to the first enclosure during combustion of the extinguishable solid propellant. Control means. (8) A removable isolation plug associated with the pressure control means to seal the pressure control means until combustion of the extinguishable solid propellant. (9) Means for removing the plug means associated with the combustion of extinguishable solid propellant. (10) A transportation means intermediate the second and third enclosures for transporting the gas generated in the third enclosure to the release means in the second enclosure. (11) Gas pressure control means associated with the conveying means for maintaining a closed gas flow from the third enclosure to the second enclosure during gas generation and intermediate between the second and third enclosures. 2. The method according to claim 1, further comprising means for ending the generation of gas by the gas generating propellant, and the second ignition means having a plurality of ignition capabilities. Multiple propellant solid rocket engine. 3. A multi-propellant solid rocket engine as set forth in claim 1 wherein said release means in said second enclosure comprises a diffuser. 4. The multi-propellant solid rocket engine according to claim 1, further comprising a partition wall between the first and second enclosures. 5. The pressure control means comprises a hole in the bulkhead between the first and second enclosures, the hole extending from the second enclosure to the first enclosure for burning the extinguishable solid propellant. A multi-propellant solid rocket engine as set forth in claim 4 having an active area for maintaining a propellant combustion gas blocked therein. 6. A multi-propellant solid as claimed in claim 5, wherein the plug means comprises an isolated diaphragm closing the bulkhead hole and the means for removing the plug means comprises explosive means. Rocket engine. 7. A multi-propellant solid rocket engine as set forth in claim 1 further including rocket attitude control means driven by controlled combustion of the gas generating propellant. 8. A multi-propellant solid rocket engine characterized by including the following elements: (1) A first casing containing a solid speed-up engine and an adjoining, controllable, solid, rear stage speed-up engine. (2) The bulkhead has a hole therein that delimits a nozzle for controlling the post-acceleration pressure, the nozzle providing communication between the acceleration engine and the post-acceleration engine during operation of the post-acceleration engine. And a post-acceleration pressure control nozzle having a first area such that the propellant combustion gas flow through the pressure control nozzle remains blocked during the post-acceleration operation. An internal partition wall in the middle of the rear speed-up engine. (3) An isolated rupture diaphragm that closes the bulkhead hole, thereby preventing premature ignition of the rear booster engine. (4) Explosion means for rupturing the diaphragm in association with the operation of the latter stage speed-up engine. (5) High-energy propellant particles within the speed-increasing engine region for preparing an initial high-thrust or initial impulse accelerating pulse. (6) Speed-up engine A speed-up igniter for igniting propellant particles. (7) A fully axially movable nozzle associated with the first casing for providing thrust vector control and having a second area greater than the first area. (8) A nozzle actuator operably associated with the moveable nozzle for controllably moving the nozzle in all axial directions. (9) The above-mentioned post-stage acceleration engine, which includes an extinguishable propellant particle for preparing a stop and start operation for the post-stage acceleration engine and a diffuser for distributing an ignition gas to the extinguishable propellant particle. (10) Gas generator propellant particles, and a gas generator for post-stage acceleration engine ignition including a gas generator dual igniter for repetitive ignition of gas generator particles for the production of gas Second gas casing. (11) A multiport type flow control valve having an inlet and having at least a first outlet and a second outlet for controlling the gas flow from the gas generator. (12) Gas flow from the gas generator to the flow control valve to the gas generator and the inlet, gas from the gas generator to the ignition and throttling of the rear stage acceleration engine to the diffuser and the rear stage acceleration engine through the flow control valve First outlet and diffuser for flow,
A branch pipe that operatively connects the second outlet to the outside of the flow control valve for gas emission due to rapid pressure drop of the gas generator and extinguishing of the gas generator propellant particles. (13) It seems that the gas flow through the flow control valve remains blocked against the ignition and throttle of the post-acceleration engine during the post-acceleration operation, and remains blocked against the extinction of the post-acceleration engine. A flow control valve that provides a variable flow direction and variable operating area from full open to closed. 9. A multi-propellant solid rocket engine as claimed in claim 8 wherein the post-acceleration engine propellant particles comprise non-metallized carbon fluoride type propellant. 10. The isolated burst diaphragm is integral with the bulkhead such that a linearly charged explosion opens the bulkhead to form a post boost pressure control nozzle. A multi-propellant solid rocket engine according to claim 8. 11. A multi-propellant solid rocket engine characterized by including the following elements: (1) A first casing including a solid speed-up engine and an adjoining, controllable, solid, rear stage speed-up engine. (2) The partition wall has a hole therein which delimits a nozzle for controlling the post-acceleration pressure, and the nozzle forms a connection between the acceleration engine and the post-acceleration engine during operation of the post-acceleration engine. And a post-acceleration pressure control nozzle having a first area such that the propellant gas flow through the pressure control nozzle remains blocked during the post-acceleration operation. The internal partition wall in the middle of the speed-up engine. (3) An isolated rupture diaphragm that closes the bulkhead hole, thereby preventing premature ignition of the rear booster engine. (4) Explosion means for rupturing the diaphragm in association with the operation of the latter stage speed-up engine. (5) High-energy accelerating engine propellant particles in the accelerating engine region for preparing an initial high thrust or an initial impulse accelerating pulse. (6) Speed-up engine A speed-up igniter in the speed-up engine range for igniting propellant particles. (7) A fully axially movable nozzle associated with the first cylindrical casing and having a second area larger than the first area for providing thrust vector control by discharge of propellant combustion gases. (8) A nozzle actuator operably associated with the moveable nozzle for controllably moving the nozzle in all axial directions. (9) Diffuser. (10) A rear speed increasing engine including extinguishable propellant particles for supplying stop and start operations to the rear speed increasing engine, and the rear speed increasing engine for supplying gas to the extinguishable propellant particles. The above diffuser associated. (11) Gas generating multiple igniters. (12) A second cylindrical casing containing a gas generator propellant particle and a gas generator for ignition and attitude control of a post-acceleration engine, and repetitive ignition of the gas generator propellant particle and generation gas. A gas generator multi-igniter as defined above in connection with a gas generator as defined above. (13) A multiport type flow control valve for controlling the generated gas flow, which has an inlet, a first outlet, a second outlet, and a plurality of attitude control outlets. (14) Attitude control device including a plurality of gas outlets. (15) Attitude control outlet of rocket attitude control and attitude control outlet of flow control valve, gas generator and exit for gas flow from gas generator to flow control valve, ignition and throttle of post-accelerating engine First outlet and diffuser for the gas flow from the gas generator to the downstream engine and diffuser through the flow control valve, gas emission and gas generation from the gas generator due to the rapid pressure drop of the gas generator A branch pipe that operatively connects the second outlet for extinguishing the granules and the outside of the flow control valve. (16) Variable flow direction from full open to closed so that the gas flow through the flow control valve remains blocked during operation of the post-acceleration engine and when it is closed the combustion of the post-acceleration engine is extinguished. And a flow control valve with variable operating area.